EP2088290B1 - Versteifender Gehäuseabreibbelag in einem Turbotriebwerk - Google Patents

Versteifender Gehäuseabreibbelag in einem Turbotriebwerk Download PDF

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Publication number
EP2088290B1
EP2088290B1 EP08168910A EP08168910A EP2088290B1 EP 2088290 B1 EP2088290 B1 EP 2088290B1 EP 08168910 A EP08168910 A EP 08168910A EP 08168910 A EP08168910 A EP 08168910A EP 2088290 B1 EP2088290 B1 EP 2088290B1
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EP
European Patent Office
Prior art keywords
downstream
panel according
laminated structure
panel
panels
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP08168910A
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English (en)
French (fr)
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EP2088290A1 (de
Inventor
François Marlin
Philippe Verseux
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
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SNECMA SAS
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Publication date
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Publication of EP2088290A1 publication Critical patent/EP2088290A1/de
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Publication of EP2088290B1 publication Critical patent/EP2088290B1/de
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/047—Heating to prevent icing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to a panel supporting a layer of abradable material and to a turbomachine comprising such panels.
  • a turbofan engine comprises a fan wheel at its upstream end, which carries a plurality of blades and which rotates in a fan casing.
  • a cone arranged upstream of the blower wheel makes it possible to direct the flow of incoming air through the vanes of the blower.
  • a coating of abradable material is disposed at the right of the blades of the fan and is carried by the radially inner face of the fan casing.
  • frost forms on the surface of the cone and at the radially inner ends of the blade blades. Under the effect of the centrifugal force, pieces of ice are ejected and then collide with the part of the fan casing located downstream of the abradable.
  • protective panels require reducing the axial extent of the soundproofing panels, which contributes to increasing the sound level emitted by the turbomachine when it would be desirable to reduce it.
  • the protective panels must be made of a block with the soundproofing panels, which complicates their manufacture and increases their cost.
  • the replacement of a protective panel requires the replacement of the soundproofing panel which is integral, which increases in a manner costs because the soundproofing panels are difficult to manufacture and therefore expensive.
  • wide-blade blades ie blades with a curved section
  • straight blades are preferred over straight blades since they make it possible, owing to their more advanced aerodynamic shape, to improve the efficiency of the blower and especially to better resist flying impacts of foreign bodies, such as for example volatile.
  • the invention aims in particular to provide a simple, economical and effective solution to these various problems.
  • an abradable support panel for a turbojet comprising a rigid support intended to be fixed on an inner wall of a fan casing and one side of which is covered with a laminated structure carrying a layer of abradable material.
  • said laminated structure comprising fiber webs embedded in a polymer, characterized in that the laminate structure comprises a first or upstream portion covered by the abradable and a second or downstream portion extending beyond the abradable, the thickness of the downstream part being greater than that of the upstream part and being able to withstand ice impacts.
  • the panel bearing the abradable which carries the downstream protection and not the soundproofing panels arranged downstream.
  • the dissociation of the protection and soundproofing panels makes it possible to simplify the manufacture of the protection panels, and to limit the cost of maintenance operations since the replacement of the laminated downstream part no longer necessarily requires the replacement of the soundproofing panels.
  • the upstream portion of the laminated structure is of constant thickness over a major part of its length, and is connected to the downstream part by an area whose thickness increases progressively downstream.
  • This thickness makes it possible to protect the majority of the crankcase subjected to the impacts of ice.
  • the upstream portion of the laminate structure which is of constant thickness extends over approximately two-thirds of the axial dimension of the abradable.
  • the rigid support is preferably with a cellular structure and may comprise two superimposed layers, also with a cellular structure, separated by a plate.
  • This honeycomb structure is particularly interesting because it is lightweight and easily replaceable during a maintenance operation. In addition, it also has the advantage of distributing the energy released by an ice impact on the laminated structure over a large area, thereby increasing the lifetime of the entire abradable support panel. .
  • the cells carrying the downstream portion of the laminated structure advantageously have sections smaller than those of the cells carrying the upstream portion of the laminated structure.
  • the cells of the upstream and downstream ends of the support are closed by a layer of a polymer foam.
  • the upstream and downstream parts of the stratified structure may comprise a stack of 4 to 7 fiber webs and 11 to 18 fiber webs, respectively, and the fiber webs may be fiberglass webs embedded in an epoxy resin.
  • the rigid support may be honeycomb and the panel may have a cylindrical or conical sector shape.
  • the invention also relates to a turbojet engine nacelle, characterized in that it comprises abradable support panels of the type described above.
  • the nacelle may comprise between 4 and 6 abradable support panels mounted end to end.
  • the invention also relates to an aircraft turbojet, characterized in that it comprises abradable support panels of the type described above, arranged at the right of the blades of the fan so that the downstream parts of the laminated structures these panels extend downstream of the blades of the fan to soundproofing panels.
  • FIG 1 represents a blower 10 of axis turbojet engine 12, comprising a wheel formed of a disc 14 carrying at its periphery a plurality of blades 16 whose feet are engaged in grooves of the disc 14 and whose blades 18 extend radially outwardly in the direction of a fan casing 20 carrying a nacelle 22 surrounding the vanes 16 externally.
  • the fan wheel is rotated about the axis of the turbomachine 12 by a shaft 24 fixed by bolting 26 to a frustoconical wall 28 integral with the fan wheel.
  • the shaft 24 is supported and guided by a bearing 30 which is carried by the upstream end of an annular support 32 attached downstream to an intermediate casing (not shown) disposed downstream of a low-pressure compressor 34 whose rotor 36 is secured to the blower wheel via a connecting wall 38.
  • An inlet cone 40 is mounted at the upstream end of the turbojet to divert the incoming air flow to the fan blades 16.
  • the fan casing 20 comprises on an inner face a coating of abradable material 42 disposed at the right of the fan blades 16 and intended to wear during contact with the radially outer ends of the blades 16. This layer of abradable material 42 reduces the clearance between the tops of the blades 16 and the fan casing 20 and thus optimize the performance of the turbomachine.
  • a protection panel 44 is mounted downstream of the abradable layer 42 and is secured at its downstream end with a soundproofing panel 46.
  • the protection panel 44 is fixed to the casing 20 by means of radial pads 48.
  • the frost accumulated on the surface of the cone 40 and the radially inner ends of the vanes 16 is ejected into the air inlet duct under the effect of the centrifugal force and collides with the panel 44, which protects the casing from the impacts of ice cream.
  • the radial pads 48 allow to damp some of the energy released by the ice impacts.
  • the impact zone extends not only downstream of the abradable 42 but also on a portion of the abradable 42 located at the blade, and the use of a Protection panel 44 downstream of the abradable 42 does not effectively protect the entire area of the housing 20 subjected to ice impacts.
  • the invention thus overcomes these problems as well as those mentioned above by integrating the protection against ice impacts to a support panel of the abradable.
  • a laminated structure 50 comprising fiber layers embedded in a polymer covers the inner face of a rigid support 52 fixed to the fan casing and comprises an upstream portion 54 carrying the abradable 42 and a downstream portion 56 extending beyond the abradable 42.
  • the upstream portion 54 of the laminated structure 50 has a constant thickness over most of its axial dimension and is connected to the downstream portion 56 by a zone 57 whose thickness increases progressively downstream.
  • the downstream portion 56 of the laminate structure 50 has a thickness greater than that of the upstream portion 54 and thus constitutes a protective layer to ice impacts.
  • the rigid support 52 has a honeycomb structure whose upstream and downstream ends are closed by a layer of foam 58 polymer.
  • This honeycomb structure may have cells 60 of identical dimensions along its entire length ( figure 3 ).
  • the cells 62 carrying the downstream portion 56 of the laminated structure 50 may have sections smaller than those of the cells 64 carrying the upstream portion 54 of the laminated structure 50. Indeed, the majority of the impacts being in the downstream portion 56 of the laminated structure 50, it is preferable to reduce the section of the cells carrying the downstream portion 56 of the laminated structure 50 , so that the energy of an impact of a piece of ice is transmitted to a maximum of cells 62 ( figure 4 ).
  • a rigid support 52 comprising two superposed layers with a honeycomb structure, one of which is radially external 66 is fixed to the fan casing 20 and the other radially inner 68 carries the laminated structure 50.
  • the inner 68 and outer 66 stages are separated by a plate 70.
  • the cells 72 of the radially outer stage 66 all have the same section, while the cells 74 of the radially inner stage 68 which are fixed to the downstream part 56 of the laminated structure have a smaller section than that of the cells 76 of the same stage carrying the upstream portion 54 of the laminated structure.
  • a honeycomb structure has the advantage of better transmitting the impact energy of a piece of ice compared to a foam where the energy released during the impact remains concentrated locally.
  • the radial clearance between the casing 20 and the blades 16 must be large, for example of the order of 25 to 50 mm, it is preferable to make the cellular structure 52 in two stages so that the operator during a maintenance operation can replace only the radially inner stage.
  • the honeycomb structure 52 is a honeycomb type structure and the fiber plies are layers of fibers of glass embedded in an epoxy resin.
  • the upstream and downstream portions 54 of the laminated structure 50 comprise a stack of 4 to 7 layers of fibers and a stack of 11 to 18 layers of fibers, respectively, and the transition of variable thickness between the upstream portions 54 and downstream 56 of the laminated structure 50 has an axial dimension of 1 to 2 centimeters.
  • the abradable support panel is made by placing several layers of fiber sheets on a honeycomb structure 52 so as to have a greater thickness downstream of the panel than upstream of the panel.
  • Each sheet of glass fibers having a preferred orientation of its constituent fibers it is possible to stack the sheets so that the fibers of a sheet make an angle of 45 ° with the fibers of the upper or lower sheet. This arrangement makes it possible to increase the rigidity of the laminated layer 50 after passing through an oven for polymerization and hardening of the layers of fibers.
  • the free face of the honeycomb structure is then bonded to an inner face of the fan casing 20 and the abradable layer 42 intended to come into contact with the radially outer ends of the blades 16 is applied to the inner surface of the upstream portion 54 of the laminate structure 50 by means of a spatula, for example, so that the downstream end of the abradable layer 42 is in contact with the upstream end of the downstream portion 56 of the laminated structure 50.
  • the panel may be in the form of a cylindrical or conical sector and the nacelle 22 may comprise between 4 and 6 sectors of panels mounted end-to-end.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (15)

  1. Abriebschicht-Trägerplatte für Turbotriebwerke, bestehend aus einem starren Träger (52), der dazu vorgesehen ist, an einer Innenwand eines Gebläsegehäuses (20) befestigt zu werden, und dessen eine Seite mit einer Schichtstruktur (50) beschichtet ist, die eine Schicht aus abriebfähigem Werkstoff (42) trägt, wobei diese Schichtstruktur (50) in einem Polymer versenkte Fasergeflechte umfasst,
    dadurch gekennzeichnet,
    dass die Schichtstruktur (50) einen ersten Teil oder vorderen Teil (54) enthält, der mit dem abriebfähigen Werkstoff beschichtet ist, und einen zweiten Teil oder hinteren Teil (56) enthält, der sich über den abriebfähigen Werkstoff (42) hinaus erstreckt, wobei die Stärke des hinteren Teils (56) größer ist als die des vorderen Teils (54) und geeignet ist, dem Aufschlagen von Eisstücken standzuhalten.
  2. Platte nach Anspruch 1,
    dadurch gekennzeichnet,
    dass der vordere Teil (54) der Schichtstruktur (50) über den größten Teil seiner Länge von gleich bleibender Stärke ist und mit dem hinteren Teil (56) durch einen Bereich verbunden ist, dessen Stärke nach hinten fortschreitend wächst.
  3. Platte nach Anspruch 2,
    dadurch gekennzeichnet,
    dass sich der vordere Teil (54) mit gleich bleibender Stärke über ungefähr zwei Drittel der axialen Abmessung des abriebfähigen Werkstoffs (42) erstreckt.
  4. Platte nach einem der Ansprüche 1 bis 3,
    dadurch gekennzeichnet,
    dass der starre Träger (52) ein zellenförmiger Aufbau ist.
  5. Platte nach Anspruch 4,
    dadurch gekennzeichnet,
    dass der starre Träger (52) zwei übereinander liegend angeordnete Etagen (66, 68) mit zellenförmigem Aufbau enthält, die durch eine Platte (70) voneinander getrennt sind.
  6. Platte nach Anspruch 4 oder 5,
    dadurch gekennzeichnet,
    dass die Zellen (62, 74), die den hinteren Teil (56) der Schichtstruktur (50) tragen, kleinere Unterteilungen haben als die der Zellen (64, 76), die den vorderen Teil (54) der Schichtstruktur (50) tragen.
  7. Platte nach einem der Ansprüche 4 bis 6,
    dadurch gekennzeichnet,
    dass die Zellen des vorderen und des hinteren Endes des Trägers durch eine Schicht aus einem Polymerschaum (58) verschlossen sind.
  8. Platte nach einem der Ansprüche 1 bis 7,
    dadurch gekennzeichnet,
    dass der starre Träger (52) wabenförmig ausgeführt ist.
  9. Platte nach einem der Ansprüche 1 bis 8,
    dadurch gekennzeichnet,
    dass der vordere Teil (54) der Schichtstruktur (50) einen Stapel von 4 bis 7 Fasergeflechten umfasst.
  10. Platte nach einem der vorherigen Ansprüche,
    dadurch gekennzeichnet,
    dass der hintere Teil (56) der Schichtstruktur (50) einen Stapel von 11 bis 18 Fasergeflechten umfasst.
  11. Platte nach einem der vorherigen Ansprüche,
    dadurch gekennzeichnet,
    dass die Fasergeflechte Glasfasergeflechte sind, die in einem Epoxidharz versenkt sind.
  12. Platte nach einem der vorherigen Ansprüche,
    dadurch gekennzeichnet,
    dass sie die Form eines zylindrischen oder konischen Sektors hat.
  13. Gondel eines Turbotriebwerks,
    dadurch gekennzeichnet,
    dass sie Abriebschicht-Trägerplatten nach einem der Ansprüche 1 bis 12 aufweist.
  14. Gondel nach Anspruch 13,
    dadurch gekennzeichnet,
    dass sie 4 bis 6 Platten aufweist, die mit den Enden aneinandergrenzend angebracht sind.
  15. Flugzeug-Turbotriebwerk,
    dadurch gekennzeichnet,
    dass es Abriebschicht-Trägerplatten nach einem der Ansprüche 1 bis 12 aufweist, die in Verlängerung vor den Schaufeln (16) des Gebläses (10) dergestalt angeordnet sind, dass sich die hinteren Teile (56) der Schichtstrukturen (50) dieser Platten hinter den Gebläseschaufeln (16) bis hin zu Schalldämmungsplatten erstrecken.
EP08168910A 2007-12-14 2008-11-12 Versteifender Gehäuseabreibbelag in einem Turbotriebwerk Active EP2088290B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0708712A FR2925118B1 (fr) 2007-12-14 2007-12-14 Panneau de support d'abradable dans une turbomachine

Publications (2)

Publication Number Publication Date
EP2088290A1 EP2088290A1 (de) 2009-08-12
EP2088290B1 true EP2088290B1 (de) 2012-04-11

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Country Status (6)

Country Link
US (1) US8061967B2 (de)
EP (1) EP2088290B1 (de)
CN (1) CN101457771B (de)
CA (1) CA2646970C (de)
FR (1) FR2925118B1 (de)
RU (1) RU2477805C2 (de)

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Publication number Priority date Publication date Assignee Title
DE102015113685A1 (de) 2014-11-27 2016-06-02 East-4D Carbon Technology Gmbh Luftleit- und Lärmschutzeinrichtung in einem Zweistrom-Strahltriebwerk und Verfahren zu deren Montage
DE102015113685B4 (de) 2014-11-27 2020-08-06 East-4D Carbon Technology Gmbh Luftleit- und Lärmschutzeinrichtung in einem Zweistrom-Strahltriebwerk und Verfahren zu deren Montage

Also Published As

Publication number Publication date
CA2646970C (fr) 2015-11-17
US20100329843A1 (en) 2010-12-30
RU2477805C2 (ru) 2013-03-20
EP2088290A1 (de) 2009-08-12
FR2925118B1 (fr) 2009-12-25
RU2008149143A (ru) 2010-06-20
FR2925118A1 (fr) 2009-06-19
CN101457771A (zh) 2009-06-17
CA2646970A1 (fr) 2009-06-14
US8061967B2 (en) 2011-11-22
CN101457771B (zh) 2012-10-10

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